Self-aligning loading rail



A. J. GABoRc ETAL 3,099,936

Aug. 6, 1963 sELF-ALIGNING LOADING RAIL Filed Feb. 27, 1961 5 Sheets-Sheet l FIG. .1

FIG. 2

@Hummm www@ 23 24M 26/ INVENTORS Arf/wr J. Gaborc Mofa Teum/m i o@ l@ATTORNEYS AGENT Aug- 6, 1963 A. J. GABoRc ETAL 3,099,936

SELF-ALIGNING LOADING RAIL Filed Feb. 27, 1961 5 Sheets-Sheet 2 AGENT United States Patent O The present invention relates generally to missile launchers and more particularly to an improved selfaligning loading-rail for a missile launcher.

With the advent of high performance turbo-jet, ram-jet and rocket propelled aircraft came the obsolescence of conventional anti-aircraft guns. Guided missiles traveling at speeds above Mach 1 .and 2 with infra-red and radar homing systems have proved to be the only anti-aircraft weapons eifective against these high performance aircraft.

lIn order to protect ground troops from bombing and strafing by these high performance aircraft these missile launching systems must have a high degree of mobility. Accordingly, missile launchers have been mounted on truck or trailer beds and kept at all times in the vicinity `of the ground Itroops which they are supporting.

The missiles launched by many of these launchers are of considerable weight and must be transferred automatically from the missile transporting means to the launcher. Such a transfer system has been developed and is the subject matter of patent application, Serial No. 357,937, tiled May 27, 1953, now U.S. Patent 2,978,959, by Robert E. Carlberg. Both this application and the present application 'have a common assignee.

In that device the missile launchingsystem is mounted directly on the ground or on a mobile carriage which is capable of being moved from position to position within a battle area. Problems have been encountered in loading the missiles onto the launcher arm rail because, in many instances, the surface of the ground below this rail .is often irregular. More speciically, when the `truck or trailer is moving to a position beneath the rail during the transfer operation the truck carriage is caused-to pitch and roll with the surface of the groundthereby making it dif- `ticult to load the missile onto the rail. ln many instances,

one of the two lugs on the missile will become properly positioned on the rail While the other will not. Further, when both lugs do properlyengage the `rail it is often difficult to precisely stop the loading truck at the exact position when proper engagement of the missile with the rail is attained. Thus, over-running occurs thereby causing one or more of the lugs to be severed from the missile or damage to the loading carriage and the missile launching arm.

Accordingly, it is an object of the present invention to provide an improved self-aligning loading rail.

A further object of the present invention resides in the improved means for aligning a missile launcher rail with a missile.

A still further object of the present invention provides a means to obviate launcher rail or missile damage due to over-run of the =loading vehicle.

Another object of the present invention provides a means whereby a missile is securely stored on a missile launcher.

A still further object of the present inventionis to provide a self-alignable guide means for `a missile launcher which is simple in construction, reliable in operation, and relatively `inexpensive in cost.

Other objects and many of the attendantadvantages of this invention will be readily appreciated as the same becomes better understood by reference to the `following 3,099,936 Patented Aug. 6, 1963 ice detailed description when considered in connection with the accompanying drawings wherein:

FIG. 1 is a side view of a missile launcher having a missile positioned thereon;

FIG. 2 -is a side View partlally in section showing a missile about -to be transferred from the loading carriage to the launcher arm;

FIG.,3 lis a side View partially in section of the U-lug way assembly;

`FIG. 4 is =a fragmentary perspective view of the front end of the U-lug Way assembly;

i |FIG. 5 is a sectional .View along a line substantially corresponding to line 5--5 of FIG. 3;

FIG. 6 is a side view, partially `in section, of the T-lug .way assembly;

FIG. 7 is a sectional view along a line substantially `corresponding to line7-7 of FIG. 6i; and

FIG. 8 is a fragmentary perspective view of the rail p alignment blocks.

In the embodiment of the present invention, as illustrated in FG. 1, a mobile missile `launcher 11 has had its front and rear carriages or bogie asssemblies, not shown, removed. The base or stand 12 of the missile launcher 11 has bogie dudgeons 1^3 to which thebogie assemblies maybe attached. The stand is provided with a pedestal 14 rigidly secured thereto and a trunnion support 15 rotatably mounted thereon. A trunnion tube 16 is supported by the trunnion support 15 and is operable to vertically rotate or elevate the arm 17. While only one ,arm 17 is shown `mounted on the trunnion tube l16, the normal arrangement provides `an arm on each side of the trunnion support 15. A guided missile 18 with its associated booster 18a and having a forward U-lug 19 and an aft T-lug 20 is received, stored, and launched by the rail which is suitably mounted on the arm 17. The term missile as used hereinafter is defined as including a missile with or without Van associated booster. iDuring operation of the system, signals received from the re control system, not shown, `are amplified and used to train or horizontally rotate the trunnion support 15 about pedestal `14- and to elevate the arm 17 thereby aiming the missile in the desired launch direction.

It is emphasized that theinstant invention is applicable to any missile launcher which `is to be loaded from a `carriage `which must move over an irregular surface dur- `mounting 25, and an aft T-lug mounting 26|. The rail 22 is secured to the arm 17 by substantially identical linkage systems wherein sway links 31a and 31h having sway connections 32 therein are connected to the lift rod 33.

The sway links 31a and 3111 have sway Iconnections 32 positioned therein in a manner to permit rotary and lateral movements While prohibiting longitudinal movement of rthe rail. Lift `rod 33 has ia collar `34 rigidly secured thereto. `Guide means 35 restricts lateral movement of the lift rod 33 while stop means 36 `prevents downward movement of the lift rod 33` below the position shown in FIG. 2. Thecollar 34 has one endet thrust absorbing link 37 pivotally connected thereto while. the other end of `link 37 is pivotally connected `to the stationary pivot 38. Link 37 opposes `the bending forces applied to the lift rod 33 'by link `44 land motor 47. Ille connection between collar 34 `and link 37 is `such as to compensate for the rotation of link 37. Bell crank link `41 has its ends pivotally connected tothe ,stationary pivot `ft2 and the link 43 at pivot 41a. The link 41 is pvotally connected at 4117, `through link `4x4, to the missile heightcompensator therefore the 45 which normally acts as a rigid connection between the link 43 and the output shaft 46 of the uid motor 47. y'I'he piston 48 of the uid motor 47 is reciprocated in response tovrluid pressure llowing to and from the motor 47 via conduits 49 and 50. Guides 51 restzain the movement of the missile height Icompensators 45 and the Huid motor output shafts 46 to a linear direction.

Each height compensator 45 has a shaft 52 which is rigidly secured to the compensator housing. A piston or slide 53 is connected to the shaft 46 and has a spring 54 connected thereto. The spring 54 is also rigidly secured to the end of the compensator housing and under normal load-ing, as mentioned hereinbefore, the height compensator acts as -a rigid connection. However, when the linkage is subjected to the unusually ln'gh forces the piston will stress the spring 54 and the height compensation 45 will absorb the movement ygenerated -by this force. Only the linkage system at the left band of farm 17, as shown in FIG. 2, has been completely described as the linkage at the opposite end of the Iarm 17 is substantially identical.

Rail 22 has a forwardly positioned U-lug way assembly 60, FIGS. 3-5, and an aft positioned T-lug way assembly 70, FIGS. 6-7, which are operable to receive the correspondingly mounted missile lugs. For reasons of clarity, the U-lug way and T-lug assemblies 60 and 70 Iare not shown in FIGS. 1 and 2. The U-lug way assembly 60 has an entrance cam 61 which guides the U-lug 19 into the ways lor grooves 62 which vertically support the U-lug 19 and, therefore, the missile. A U-lug feeler bar 63 is positioned cn one side of the assembly 60 and is supported by parallel links 64. The reeler bar 63 is biased by spring 64 and link 65 in a downward direction in Ia manner whereby insertion sfo the U-lug 19 into the grooves or ways 62 effects upward movement of the feeler bar and actuation of switch 66. The ways or grooves 62 are continuous along each side `of the assembly -60 thereby permitting the U-lug 4to pass from one end of the assembly to the other without restriction.

A fir-ing cont-act 67 in the form of a laminated leaf spring is mounted on one side of the U-lng way assembly 60 and contacts the U-lug 19 of the missile when the lug is in the ram position, as shown by the dotted lines in FIG. 3. Guards `68 and 69 are provided on either side of the contact in order to protect this contact during loading from damage which might result from a lug which does not engage the grooves or ways.

The T-lug way assembly 70 has -an entrance cam 71 which guides the missile T-lng 20 into the T-shaped groove or way 72, which vertically supports the T-lug and missile. The T-lug way assembly 70 includes a ram link 73 which pivots about connection 74, as shown in FIG. 6. A roller 75 is suitably mounted on the lower end of the ram link 73 and is effective to reduce friction and possible damage when the ram link 73 contacts the T-lug 20 during the ramming operation. 'Ilhe ram link 73 is positioned by the fluid motor 76 which acts through .a ram piston shaft 77. A latch 78 is biased downwandly by spring 79 and automatically locks the shaft 77 in its retracted position .as shown in FIG. 6. Means, not shown, are provided to retract the latch from its shaft locking position.

FIGS. 6 and 7 illustrate the firing latch mechanism 81 Y which includes a shear tipi 82 which is camrned upwandly by movement of -the T-lng in the loading direction, e.g. to

the right in FIG. 6. The shear tip 82 is mounted on the member 83 which is pivotally connected to the rail by pin 84. Spring means -85 biases the member in the clockwise direction, as viewed in FIG. 7, while permitting the shear tip 82 and the member 83 to be cammed in a counterclockwise direction by the movement thereunder of the T-lug in lthe loading direction. An output shaft 87 having a lost motion connection -88 therein connects the motor 89 with the link 90. Link 90 s in turn connected to the member 83. When the shaft 87 is in its upper-most position Ias shown in FIG. 7, the lost motion connection 88 permits limited counter-clockwise rotation of member 83 and the shear tip 82 thereby permitting the T-lug 20 to cam the shear tip upwardly out of its path. However, when the motor 89 positions shaft 87 in its lower-mo-st position the lost motion connection 88 is taken-up and the member 83 and shear tip 82 are locked against counter-clockwise movement. Lever 91 is associated with the shaft 87 while lever 92 is associated with link 90. The levers '91 and 92 operate switches 93 and 94 respectively thereby indicating the position of the shaft 87 and member 83 on the launcher control panel, not shown.

The rear release latch 101 as shown in FIG. 6, is pivotally connected to the rail 22 by pin 102 and to the rear release link 103 by pin 104. Pivotally connected to the rear release link 103 by pin 105 is the rear release switch cam 1016. As the missile T-lug 20 bears against the rear release latch 101, the resulting motion of the latch 101 moves the rear release link 103 upward causing the rear release switch cam `106 to actuate the release switch 107. Rear release spring 108 is interposed between the nail 22 and the rear release link 103 in the manner shown in FIG. 6. 'I'he roller 108 is positioned at the upper end of .the rear release link 103 and contacts the portion 109 of the arm 17 when the rail 22 is raised to Ithe bring position as will be explained in more detail hereinafter. When the loading tnuck 23 has overrun the rail 22 the lug 20 (forces the rear release latch 101 in a connterclockwise direction, as viewed in FIG. 6, thereby camming the latch out of its path. Thereafter, the lug 20 is free and continues through the T-lug way 72 thereby obviating any damage to the missile lugs 19 or 20 or to the way assembly 70. Inother words, the rear release mechanism permits removing of the missile from the rail by allowing the truck to drive the missile lugs through the ways 62 and 72. However, when the rail assembly is raised to the ring position the rear release link 103| is locked again-st movement by contact of the roller 108 with the portion 109 or arm 17. Consequently the rear release latch 101 is positively locked against motion.

FIG. 8 illustrates one embodiment of alignment blocks 111 and 112 which may be used to properly position the rail `22 with respect tothe arm 17 when the system is in the raised or rng position. The alignment blocks oonsi'st of a set of mating V-block-s 113 and 114 at each end of the sway link 31. These blocks insure accurate location of the rail 22 when in the raised position. 'Ihe female block 113 is securely fastened by conventional fastening means 115 to the arm. This female block 113 has inwardly sloping smvtaces 16 which will engage the complementary cam surface 117 of the male V-blocks 114. 'I'lie male V-blocks are adjusted in a direction toward and away from the Isway length 31 by turning of the bolts 11:8 thereby moving the V-blocks with respect to the base plate I119. Shims 121 interposed between the base plate 119 and the rai-l 22 adjust the height of the rail with respect to the arm when the nail is in the raised position.

In operation, 'when it is desired to load a missile onto the rail 22 the iluid motor v47 is actuated thereby moving its associated linkage to the position shown in FIG. 2, that is, moving the rail to a lowered position. In this position due :to the sway links 31a and 31b the rail may be moved with respect to its axis angularly, radially, or any combination of these directions. When the rail 22 in the lowered position the loading carriage or truck 23 is driven thereunder. Because surface or the ground G is often irregular, the carriage 23y and the missile loaded thereon will have roll, pitch, and yaw movements as the T-'lug and U-lug contact their respective entrance cams. The sway connection 32 permit rotary and late-ral movements of the rail 22 but prohibit longitudinal movement thereof.

More specifically, contact of lugs 19 and 20 rwith the entrance cams 61 and 71, respectively, cause the rail to notate and move laterally thereby effecting alignment of the way assembly grooves with the appropriate lugs. In order to permit the .height compensators 45 to perform properly, the rail is lprohibited from moving in an axial or longitudinal direction, as explained hereinbefore. Restraining the rail from moving in a longitudinal direction prevents the rail from backing `:away from an oncoming lug, thereby permitting .lug entry into ways `62. and72.

Should the lugs 19` and 20 be too high with respect to ways 62 Iand 72 the rail Iwill lbe cammed upwardly. This upward movement is absorbed by the one or both of the height compensators |45. For example, shouldithe forward U-lug be higher than its way -62 it will rst contact the entrance cam thereby forcing upwardly the sway link 31a, lthe link `33, collar 34 Ithereby moving linkage 44 to the right as viewed `in FIG. 2. This rightward movement will be absorbed by the height compensating device as explained hereinbefore. rPhe aft end of the rail assembly can be movedupwardly in a similar manner.

Once the lugs properly engage their way-s the U-lug feeler bar `63` and a similar feeler fbar, not shown, `in the T-lug way assembly 70 actulafte switches indicating that .the lugs are properly positioned in the ways. Then the ram llatch 78 is retracted `andthe ram uid motor 76 actuated thereby moving `output shaft `77 outwardly causing rotation of fthe nam link 73 about the pin 74 which, when the roller 75 contacts the T-f-lug, forces it in arearward direction to the rammed or ready-to-re position, as shown by the broken lines lof FIG. 6. `During movement to the ram position the T-lug 20 contacts the shear tip 82causing it to be cammed upwardly. This upward movement causes the member 83 to be rotated about pin 84 and .against the bias o-f spring `85. The lost motion connection 88 permits the member 83 to rotate in the co'nntercloclcwise direction. When the T-lug 20 `is in the ram position i-ts reanwardmovement is resisted by the rear release latch 101 which is sufficiently Ibiased by spring 108 to `permit only extremely high forces on the T-lug to `rotate it ou-t, of the way, e.g. movement of the truck. When inthe ready-to-re position forward movement of lug 20l is resisted by the shear tip 82. Once the T-lug is in the ready-tore position the ram llink 73 is retracted and locked into the retracted position. It is to be noted that the U-lug way assembly 60 supportsy the missile `only in a direction normal to the longitudinal axis of the rail and does not prevent the parallel movement of the U-lug. Once the lugs are in the ready-tothe position the rail is moved to `the raised position. In the raised position the rear release link 103 contacts the arm 17 at 109 thereby positively `locking the rear release latch and insuring tthlat the Telug, and consequently the missile, will not move in the rearward direction. When the missile booster 19 is ignited without releasing the shear tip it builds up sufficient thrust to cause the T-lug to shear or breakeoff the shear tip82 lthereby releasing the T-llug and allowing the missile Ito move forwardly from the rail 22. The normal firing procedure is `to actuate 89 to retract shear tip 82.

Dur-ing the initial loading of the missile onto the rail should one or both of the lugs 19 or 20` fail to engage its ways 162 to 72 the appropriate feeler bar would not .be actuated thereby indicating -to the control panel operator that the loading must be attempted again. The operator effects the rai-sing of the rail 22 yand the loading carriage 23 is brought Iaround for another pass.

Should the U-lug 19 engage its ways 62 'and the T-lug 2G not `so engage its ways 72. the U-lug `19 would merely pass through its ways `and out the rearward end thereof. Should T-lug 20 engage its ways 72 but the U-lug 19 not engage its ways 62 the rear release latch I101 would be contacted by the T-lug 20 Iand rota-ted in the counterclockwise direction thereby permitting the T-lug to move through its rail.

In summary, the above invention provides a completely universal loading rail which obviates diiculties encountered in loading a missile launcher from a carriage which 6 is being driven over .an-irregular surf-ace. The present system provides means to insure a high probability of initial engagement of the `miss-ile lugs with the rail assembly together with means to obviate the possibility of damage to the missile or the launcher system in case the lugs do not initially become properly engaged.

Obviously many modifications and varia-tions of the present invention are possible in the `light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1."In `alauncher `for a missile having fore and aft positioned lugs carried thereby, said launcher `comprising at least one arm member having movable rail means connected thereto, said rail means having fore and aft lugs thereon for receiving and supporting said lugs; mechanism operable to move the rail means to a missile loading position and from a missile loading position to a missile launching positionthereon, said mechanism includ-ing fore and aft lift means operatively connected to lthe -arm member and the rail means and having means operable when the rail means is in said loading position to :allow multiangular and/ or lateral movement of the rail means with respect to the longitudinal axis therefor; linkage means pivotally connected to said lift means and the arm member;

a connecting link pivoted at -one end to said linkage means;

slidably mounted compensating means for facilitating disproportionate concurrent movement of both ends of said rail moving mechanism and having the other end of the connecting link pivotally connected thereto;

uid actuated means on the arm member movable in `response to -a predetermined change in fluid pressure and operably connected to said height compensating means for actuating said lift means through -said compensating means, connecting link and the linkage means to move the rail to and from said loading :and launching positions according to the movement of the fluid actuated means, said compensating `means further including means carried by said fluid actuating means and cooperating with the compensating means for effecting independent movement of either of the lift means thereby to independently move either end of the rail means during missile loading movement; and

spring means carried by the compensating means and cooperating with said means on` the fluid actuated means for effecting proportionate movement of said lift means `from missile loading to missile `launching position `as the iiuid actuated means Vis operated by said predetermined change in iiuid pressure; and

means establishing an external pressure connection to the fluid actuated means.

2. A-launcher for -a missile as recited in claim l wherein said uid actuated means includes a casing having a pressure chamber therein,

-a piston reciprocably slidable therein,

a shaft carrying said piston and slidably supporting the compensating means; `and means on said shaft and slidably disposed within said compensating means in engagement with said spring means for actuating said compensating means, connecting link and the linkage means.

3. In -a launcher for a guided lmissile-booster combination wherein the booster has an aft T-lug and a fore U- lug mounted thereon said launcher comprising a launcher arm, movable r-ail means connected to said launcher arm, said rail means having fore and aft lug ways carr-ied thereby for receiving, -supporting and releasing said lugs;

fore and aft lift members slidably mounted on the launching arm and connected to the `rail means;

a mechanism connected to said lift members for slidably moving the lift members to actuate the rail means from missile loading position to missile launching position and from missile launching position to missile loading position, said mechanism including linkage means;

means pivotally and -drivingly connecting lthe linkage means to the lift members yand to the launching arm;

a fluid motor fixedly mounted on the launching arm;

universal joint means in said Ilift members for Iallowing angular and lateral movemen-t yof the rail means when the rail means is in a loading position;

means on said l-aunching arm and cooperating with complementary means on the rail means for preventing longitudinal movement of the rail means when the rail means is in a launching position;

height compensating means interposed between said fluid motor and Athe linkage means;

means connecting said compensation means to said linkage means;

means including a piston canried by said fluid motor and slidably supporting the compensating means for effecting independent movement of the lift means and the corresponding ends of the ra-il means should the lug strike `the rail means during movement thereof into the lug ways; and

spring means disposed within said compensating means in engagement with said piston for effecting proportionate concurrent -movement of the lift members and the rail means to missile loading position.

4. A Ilauncher for a guided missile-booster as recited in claim 3 wherein said linkage means includes first link member,

a second link member, and

a third link member,

' said vfirst link member being pivotally connected to the launcher arm and the second lin-k member, said third link member being pivotally connected to the launcher arm and pivotally connected to said second link member; y

collar means on said first lift members and cooperating with the pivoted connect-ion between the second and third link member -for providing a driving connection between the lift members and the linkages; and

an actuating rod pivotally connected to the compensating means and the second link and controlled by the fluid motor for actuating the linkage means thereby to eiect concurrent proportionate mowement of the lift members.`

5. In a launcherfor a guided missile-booster combination wherein the booster has an aft T-l-ug and a fore U-lug mounted thereon,-said launcher comprising a launcher arm, movable rail means connected to said launcher arm, said rail means having fore and aft lug ways carried thereby -for receiving; supporting and releasing said lugs;

fore and aft left members slidably mounted on the launching arm and connected to the rail means;

a mechanism connected to said lift members Ifoislidably moving the lift members to actuate the rail means `from missile loading position to missile launching position and :from missile launching position to missile loading position, said mechanism including linkage means;

means pivotally and drivingly connecting the linkage means to the lift members and to the launching arm;

a liluid motor xedly mounted on the launching arm;

universal joint means in said lift members Ifor allowing angular and lateral movement of the rail means when the rail means is in a 'loading position;

means on said launching arm. and cooperating with complementary means on the rail means for preventing longitudinal movement of the rail means when the rail means is in a launching position;

height compensating means interposed between said fluid motor and the linkage means;

means connecting said compensating means to said linkage means;

means including a piston carried by said fluid motor and slidably supporting the compensating means for effecting independent movement of the lift means and the corresponding ends of the rail means should the lug strike the rail means during move-ment thereof into the lug ways; and

spring means disposed Within said compensating means in engagement with said piston for effecting proportionate concurrent movement of the lift members and the rail means to missile loading position;

a shear tip mechanism having T-liug engaging means for restraining movement of said missile in a fforward direction and a release mechanism having T-lug engaging means for restraining movement of the missile in a rearward direction 'when the rail means is in the launching position.

6. A launcher for -a guided missile-booster combination as recited in claim 5 wherein said shear tip mechanism includes a spring biased support pivotally mounted on the rail means;

a shear tip pivotally connected to said support;

a link pivotally connected to said support;

an output shaft connected to said link, and a fluid operated device connected to the output shaft for actuating the shaft to move the shear tip out of engagement with the T-lug.

7. A launcher for guided missile-booster combination as recited in claim 5 wherein said release mechanism includes a latch member pivotally mounted on the rail means in engagement with the T-lug;

a spring biased actuating lever pivotally connected to said latch member and operated by the launcher arm to release the T-lug as the rail means reaches a missile launching position.

References Cited in the le of this patent UNITED STATES PATENTS 

1. IN A LAUNCHER FOR A MISSILE HAVING FORE AND AFT POSITIONED LUGS CARRIED THEREBY, SAID LAUNCHER COMPRISING AT LEAST ONE ARM MEMBER HAVING MOVABLE RAIL MEANS CONNECTED THERETO, SAID RAIL MEANS HAVING FORE AND AFT LUGS THEREON FOR RECEIVING AND SUPPORTING SAID LUGS; A MECHANISM OPERABLE TO MOVE THE RAIL MEANS TO A MISSILE LOADING POSITION AND FROM A MISSILE LOADING POSITION TO A MISSILE LAUNCHING POSITION THEREON, SAID MECHANISM INCLUDING FORE AND AFT LIFT MEANS OPERATIVELY CONNECTED TO THE ARM MEMBER AND THE RAIL MEANS AND HAVING MEANS OPERABLE WHEN THE RAIL MEANS IS IN SAID LOADING POSITION TO ALLOW MULTIANGULAR AND/OR LATERAL MOVEMENT OF THE RAIL MEANS WITH RESPECT TO THE LONGITUDINAL AXIS THEREFOR; LINKAGE MEANS PIVOTALLY CONNECTED TO SAID LIFT MEANS AND THE ARM MEMBER; A CONNECTING LINK PIVOTED AT ONE END TO SAID LINKAGE MEANS; SLIDABLY MOUNTED COMPENSATING MEANS FOR FACILITATING DISPROPORTIONATE CONCURRENT MOVEMENT OF BOTH ENDS OF SAID RAIL MOVING MECHANISM AND HAVING THE OTHER END OF THE CONNECTING LINK PIVOTALLY CONNECTED THERETO; 